Characteristics of Free-Piston Shock Tunnel HIEST. 1st Report. Tuned Operation of Free-Piston Driver.

勝宏, 伊藤; 智幸, 小室; 和雄, 佐藤; 修一, 植田; 英幸, 丹野; 政浩, 高橋

doi:10.1299/kikaib.68.2968

Cited by 8 publications

(1 citation statement)

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“…As discussed in the design of HIEST, because pressure and heat losses occur, numerical analysis cannot reproduce experiments without considering these effects. [15][16][17] However, this analysis assumes isentropic process to predict the maximum attainable pressure and find the optimum operational conditions. As shown in Fig.…”

Section: Compression By Free Piston and Attainable Pres-mentioning

confidence: 99%

Development of Shock Tube for Ground Testing Reentry Aerothermodynamics

Yamada

Suzuki

Takayanagi

et al. 2011

Trans. Japan Soc. Aero. S Sci.

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A free-piston double-diaphragm shock tube with 70 Â 70 mm cross-section at test section is newly developed to investigate thermochemical nonequilibrium phenomena behind a shock wave. This paper presents the performance of the shock tube and the measurement system newly developed. Experimental investigations to clarify its characteristics are conducted for various operational parameters, such as rupture pressure of the first diaphragm and initial pressures in the low-pressure tube, the high-pressure tube, and the compression tube. Based on the characteristics experiment, a performance map of the shock tube is obtained by changing the operation parameters. The result shows that the shock tube can generate the post-shock condition corresponding to super-orbital reentry flight conditions. The newly developed measurement system enables us to obtain a spatial distribution of spectra behind a shock wave with high spatial and time resolution. A description of the measurement system and typical examples of the measured spectra are presented.

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Section: Compression By Free Piston and Attainable Pres-mentioning

confidence: 99%